U.S. patent application number 14/141714 was filed with the patent office on 2015-07-02 for integral injection thrust vector control with booster attitude control system.
This patent application is currently assigned to Raytheon Company. The applicant listed for this patent is Raytheon Company. Invention is credited to Michael S Alkema, Daniel Chasman, Andrew B Facciano, Michael A Leal, Robert T Moore.
Application Number | 20150184988 14/141714 |
Document ID | / |
Family ID | 53481312 |
Filed Date | 2015-07-02 |
United States Patent
Application |
20150184988 |
Kind Code |
A1 |
Facciano; Andrew B ; et
al. |
July 2, 2015 |
INTEGRAL INJECTION THRUST VECTOR CONTROL WITH BOOSTER ATTITUDE
CONTROL SYSTEM
Abstract
A projectile includes a propulsion booster for producing
pressurized gases, a nozzle for expelling the pressurized gases
produced by the booster, and a supplementary integrated actuation
system. The integrated actuation system selectively directs
propellant from a storage reservoir of the integrated actuation
system through an interiorly-located outlet of the integrated
actuation system located at the nozzle and into the nozzle, thus
changing a direction of the pressurized gases expelled by the
booster. The integrated actuation system also selectively directs
propellant from the storage reservoir through a
peripherally-located outlet of the integrated actuation system, to
produce thrust at an external periphery of the projectile, thus
diverting the projectile. The integrated actuation system may also
selectively direct propellant to a nozzle actuation system for
positioning the nozzle, to a stage separation system for separating
portions of the projectile, or to a power generator for generating
electric power for the projectile.
Inventors: |
Facciano; Andrew B; (Tucson,
AZ) ; Alkema; Michael S; (Sahuarita, AZ) ;
Leal; Michael A; (Tucson, AZ) ; Chasman; Daniel;
(Tucson, AZ) ; Moore; Robert T; (Tucson,
AZ) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Raytheon Company |
Waltham |
MA |
US |
|
|
Assignee: |
Raytheon Company
Waltham
MA
|
Family ID: |
53481312 |
Appl. No.: |
14/141714 |
Filed: |
December 27, 2013 |
Current U.S.
Class: |
244/3.22 |
Current CPC
Class: |
F42B 10/60 20130101;
F42B 10/663 20130101; F42B 10/66 20130101; F42B 15/01 20130101 |
International
Class: |
F42B 15/01 20060101
F42B015/01 |
Claims
1. A projectile comprising: a propulsion booster for producing
pressurized gases; a central longitudinal axis that extends through
the projectile; a nozzle for expelling the pressurized gases
produced by the booster, the nozzle having a nozzle wall defining a
thrust passage for directing a thrust plume of the pressurized
gases expelled by the booster, wherein the nozzle wall has an
interior surface that faces radially inward towards the axis,
wherein the projectile has an exterior surface disposed
substantially opposite the interior surface of the nozzle, and
wherein the exterior surface faces radially outward away from the
axis; and a supplementary integrated actuation system for storing
and directing propellant, wherein the integrated actuation system
selectively directs the propellant from a storage reservoir of the
integrated actuation system to an interior outlet generally
disposed near the interior surface, thus changing a direction of
the thrust plume, and wherein the integrated actuation system
selectively directs the propellant from the storage reservoir to a
an exterior outlet generally disposed near the exterior surface, to
produce thrust at an external periphery of the projectile, thus
diverting the projectile.
2. The projectile as in claim 1, wherein the integrated actuation
system further includes: a first set of supply channels for
directing the propellant from the storage reservoir to the interior
outlet; and a second set of supply channels for directing the
propellant from the storage reservoir to the exterior outlet.
3. The projectile as in claim 1, further including: a fuselage
flange at least partially surrounding the propulsion booster;
wherein the fuselage flange defines an external opening at the
external periphery; and wherein the exterior outlet opens to the
external opening.
4. The projectile as in claim 1, wherein the propellant is a
pressurized liquid.
5. The projectile as in claim 1, wherein the booster contains a
thrust supply of propellant separated from the propellant in the
storage reservoir, wherein burning of the thrust supply of
propellant causes the thrust plume to be outwardly directed from
the nozzle wherein injection into the nozzle of propellant from the
storage reservoir alters the direction of the thrust plume relative
to the central longitudinal axis.
6. The projectile as in claim 2, further including valves for
selectively opening the first and second sets of supply
channels.
7. The projectile as in claim 1, further including valves that
control flow between the storage reservoir and the interior and
exterior outlets.
8. The projectile as in claim 1, wherein the storage reservoir
extends circumferentially around the nozzle.
9. The projectile as in claim 1, further including: a power
generator for generating electric power for the projectile using
propellant from the storage reservoir.
10. The projectile as in claim 9, further including: a manifold;
wherein the power generator is coupled between the storage
reservoir and the manifold; and wherein the power generator
generates electric power during flow of propellant between the
storage reservoir and the manifold.
11. The projectile as in claim 1, further including: a nozzle
actuation system coupled to the nozzle; wherein the integrated
actuation system selectively directs propellant from the storage
reservoir to the nozzle actuation system to position the
nozzle.
12. The projectile as in claim 1, further including: a stage
separation system for separating portions of the projectile from
one another; wherein the integrated actuation system selectively
directs propellant from the storage reservoir to the stage
separation system to selectively separate the portions of the
projectile.
13. The projectile as in claim 1, wherein the integrated actuation
system further includes a gas generator integral with the storage
reservoir for burning propellant in the storage reservoir, thereby
releasing gas into the integrated actuation system.
14. An integrated actuation system for a projectile including a
body and a nozzle coupled to the body for directing a thrust plume
expelled from the body, the integrated actuation system comprising:
a storage reservoir containing propellant; a central longitudinal
axis extending through the integrated actuation system; a radially
inward facing outlet facing radially inward towards the axis and a
radially outward facing outlet facing radially outward away from
the axis; an initial flow passage extending between the storage
reservoir and the radially inward facing outlet; and an auxiliary
flow passage extending between the storage reservoir and the
radially outward facing outlet; wherein propellant from the
integrated actuation system is selectively directed through the
initial flow passage thereby altering the direction of the thrust
plume expelled from the body relative to the central longitudinal
axis, or through the auxiliary flow passage thereby altering the
attitude and/or roll of the projectile.
15. The integrated actuation system as in claim 14, in combination
with a projectile including: the body; the nozzle coupled to the
body for directing the thrust plume expelled from the body; and a
nozzle actuation system; wherein the integrated actuation system is
operatively coupled to the nozzle actuation system for moving the
nozzle.
16. The integrated actuation system as in claim 14, in combination
with a projectile including: the body; the nozzle coupled to the
body for directing the thrust plume expelled from the body; and a
stage separation system; wherein the integrated actuation system is
operatively coupled to the stage separation system for separating
portions of the projectile from one another.
17. The integrated actuation system as in claim 14, wherein the
storage reservoir surrounds the nozzle.
18. The integrated actuation system as in claim 14, wherein the
propellant is a pressurized fluid.
19. A method of altering a flight vector of a projectile, the
method comprising: maneuvering the projectile by using fluid from a
storage reservoir of the projectile; moving fluid to a radially
inward facing outlet that faces radially inward towards a central
longitudinal axis that extends through the projectile; moving fluid
to a radially outward facing outlet that faces radially outward
away from the central longitudinal axis; altering the direction of
a thrust plume expelling from the nozzle by expelling the fluid
from the radially inward facing outlet, and/or altering the
attitude and/or roll of the projectile by expelling the fluid from
the radially outward facing outlet.
20. The method as in claim 19, further including: moving the nozzle
by moving fluid from a storage reservoir to a nozzle actuation
system for moving the nozzle.
Description
FIELD OF INVENTION
[0001] The present invention relates generally to a projectile, and
more particularly to a projectile with integrated thrust vector and
attitude control systems.
BACKGROUND
[0002] Ballistic missiles often include a flight vehicle and at
least one propulsion stage coupled to the flight vehicle. Such
ballistic missiles are often stored in a launch canister for
loading into a launch tube of a launch system, or a launcher. A
"round," a launch canister and a ballistic missile, often has a
specific and inflexible weight requirement resulting from
"load-out" capabilities of the launch system or of the armament or
vehicle where the launch system is located, such as on a warship.
The round weight requirement is divided between the launch canister
and the ballistic missile. The weight of the launch canister is
driven by the requirement for a protective launch canister, while
the weight of the ballistic missile is largely driven by the amount
of propellant and necessary componentry, such as systems of
actuators and batteries, thrust vector controls, and attitude
controls.
[0003] Such systems control separate functions of missile launch
and flight and typically have separate power sources. For example,
the propulsion stage of a projectile enables egress from a launch
canister and launch system, movement away from the launch system,
and movement towards a target. Thrust vector controls enable
control of pitch and yaw during propulsion stage burn and initial
flight vector alignment, and attitude controls enable control of
subsequent, slight pitch, yaw, and roll adjustments. These systems
also often require complex assembly integration, include numerous
single point failure sources, and add significant projectile weight
and size. Accordingly, there is a need for a projectile having
systems allowing for balancing of the projectile's external
profile, total round weight, system integration difficulty, and
failure point risk concerns.
SUMMARY OF INVENTION
[0004] According to one aspect of the invention, a projectile
includes a propulsion booster for producing pressurized gases, a
nozzle for expelling the pressurized gases produced by the booster,
and a supplementary integrated actuation system for storing and
directing propellant. The integrated actuation system selectively
directs propellant from a storage reservoir of the integrated
actuation system through an interiorly-located outlet of the
integrated actuation system located at the nozzle and into the
nozzle, thus changing a direction of the pressurized gases expelled
by the booster. The integrated actuation system also selectively
directs the propellant from the storage reservoir through a
peripherally-located outlet of the integrated actuation system, to
produce additional thrust at an external periphery of the
projectile, thus diverting the projectile.
[0005] The integrated actuation system may include a set of supply
channels for directing the propellant from the storage reservoir
out through the interiorly-located outlet and into the nozzle,
where the set of supply channels is selectively open to the
internal periphery of the nozzle, and another set of supply
channels for directing the propellant from the storage reservoir
out through the peripherally-located outlet, where the other set of
supply channels is selectively open to the external periphery of
the projectile in a direction substantially orthogonal to a
direction of thrust from the nozzle.
[0006] The projectile may include a fuselage flange at least
partially surrounding the propulsion booster, where the fuselage
flange defines an external opening, and where the
peripherally-located outlet opens to the external opening. The
propellant may be a pressurized liquid. The propulsion booster may
contain additional propellant, burning of the additional propellant
may cause a thrust plume to be outwardly directed from the nozzle,
and injection into the nozzle of propellant from the storage
reservoir may alter the direction of the thrust plume.
[0007] The projectile may include valves for selectively opening
the set of supply channels and the other set of supply channels.
The projectile may include valves that control flow between the
storage reservoir and the interiorly-located outlet and between the
storage reservoir and the peripherally-located outlet. The storage
reservoir may extend circumferentially around the nozzle.
[0008] The projectile may include a power generator for generating
electric power for the projectile using propellant from the storage
reservoir. The projectile may include a manifold, where the power
generator is coupled between the storage reservoir and the
manifold, and where the power generator generates electric power
during flow of propellant between the storage reservoir and the
manifold. The projectile may also include a nozzle actuation system
coupled to the nozzle, where the integrated actuation system
selectively directs propellant from the storage reservoir to the
nozzle actuation system, to position the nozzle.
[0009] The projectile may include a stage separation system for
separating portions of the projectile from one another, where the
integrated actuation system selectively directs propellant from the
storage reservoir to the stage separation system for separating the
portions of the projectile. The integrated actuation system may
include a gas generator attached to the storage reservoir for
burning propellant in the storage reservoir, thereby releasing gas
into the integrated actuation system.
[0010] According to another aspect of the invention, there is an
integrated actuation system for a projectile including a body and a
nozzle coupled to the body for directing a thrust plume expelled
from the body. The integrated actuation system includes a storage
reservoir containing propellant, an initial flow passage extending
between the storage reservoir and an internal periphery of the
nozzle, and an auxiliary flow passage extending between the storage
reservoir and an external periphery of the body. Propellant from
the integrated actuation system is selectively directed through the
initial flow passage thereby altering the direction of the thrust
plume expelled from the body or through the auxiliary flow passage
thereby altering the attitude and/or roll of the projectile.
[0011] The integrated actuation system in combination with a
projectile including a body, a nozzle coupled to the body for
directing a thrust plume expelled from the body, and a nozzle
actuation system. The integrated actuation system may be
operatively coupled to a nozzle actuation system for moving the
nozzle. The integrated actuation system in combination with a
projectile including a body, a nozzle coupled to the body for
directing a thrust plume expelled from the body, and a stage
separation system. The integrated actuation system may be
operatively coupled to a stage separation system for separating
portions of the projectile from one another. The storage tank may
surround the nozzle. The propellant may be a pressurized fluid.
[0012] According to yet another aspect of the invention, a method
of altering a flight vector of a projectile includes maneuvering
the projectile by using fluid from a storage reservoir of the
projectile to alter the direction of a thrust plume expelling from
the nozzle, and where movement of fluid to an external periphery of
the projectile alters the attitude and/or roll of the projectile.
The method may also include moving the nozzle by moving fluid from
a storage reservoir to a nozzle actuation system for moving the
nozzle.
[0013] The foregoing and other features of the invention are
hereinafter described in greater detail with reference to the
accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0014] The annexed drawings, which are not necessarily to scale,
show various aspects of the invention.
[0015] FIG. 1 is a cutaway view of an exemplary projectile system
including a projectile and projectile launch canister.
[0016] FIG. 2 is a partial cutaway view of the exemplary projectile
of FIG. 1.
[0017] FIG. 3 is a partially transparent perspective view of part
of the exemplary projectile of FIG. 1.
[0018] FIG. 4 is a partially transparent side view of part of the
exemplary projectile of FIG. 1.
[0019] FIG. 5 is a cross-sectional side view of part of the
exemplary projectile of FIG. 1.
[0020] FIG. 6 is a rear view of part of the exemplary projectile of
FIG. 1.
[0021] FIG. 7 is a perspective view of an integrated actuation
system for use with the exemplary projectile of FIG. 1.
[0022] FIG. 8 is a partially transparent side view of part of an
exemplary projectile showing an exemplary nozzle actuation system
with the nozzle retracted.
[0023] FIG. 9 is a cross-sectional view of the part of the
exemplary projectile of FIG. 8.
[0024] FIG. 10 is another partially transparent side view of the
part of the projectile of FIG. 8 showing the exemplary nozzle
actuation system with the nozzle extended.
[0025] FIG. 11 is another cross-sectional view of the part of the
exemplary projectile of FIG. 8.
[0026] FIG. 12 is a partially transparent side view of part of an
exemplary projectile showing a stage separation system.
[0027] FIG. 13 is a cross-sectional view of the part of the
exemplary projectile of FIG. 12.
[0028] FIG. 14 is another cross-sectional view of the part of the
exemplary projectile of FIG. 12 illustrating the stage separation
system in use.
[0029] FIG. 15 is a partially transparent side view of part of
still another exemplary projectile.
[0030] FIG. 16 is a cross-sectional view of the part of the
exemplary projectile of FIG. 15.
DETAILED DESCRIPTION
[0031] The present invention provides a projectile including a
propulsion booster for producing pressurized gases, a nozzle for
expelling the pressurized gases produced by the booster, and an
integrated actuation system integrating at least thrust vector
controls and attitude controls. The integrated actuation system
selectively directs propellant from a storage reservoir of the
integrated actuation system through an interiorly-located outlet of
the integrated actuation system located at the nozzle and into the
nozzle, thus changing a direction of the thrust from the booster.
The integrated actuation system also selectively directs propellant
from the storage reservoir through a peripherally-located outlet of
the integrated actuation system, to produce additional thrust at an
external periphery of the projectile, thus diverting the
projectile.
[0032] The integrated actuation system may also selectively direct
propellant to a nozzle actuation system for positioning the nozzle,
to a stage separation system for separating portions of the
projectile from one another, or to a power generator for generating
electric power for the projectile.
[0033] The projectile may be a missile, interceptor, vehicle,
guided projectile, or unguided projectile, and thus will be
described below chiefly in this context. The invention may also be
useful in other applications including pyrotechnics, satellites,
sub-munitions, and other booster-propelled projectiles.
[0034] Referring now in detail to the drawings and initially to
FIGS. 1 and 2, an exemplary projectile system 30 according to the
invention and for loading into a launcher is shown. The projectile
system 30 includes an outer launch canister 32 for housing or
storing a projectile 34 to be fired from the canister 32. The
projectile 34 is positioned completely interior to the launch
canister 32, although it will be appreciated that the projectile 34
may instead be positioned only partially interior to the launch
canister 32.
[0035] The projectile 34 includes a nosecone 36 for housing a
flight vehicle 40, such as a warhead, explosive, payload,
sub-projectile, sensor array, or other package. Three propulsion
stages are coupled adjacent the nosecone 36 for storing propellant
to be ignited to provide propulsion. The propulsion stages include
an upper propulsion stage 42, an intermediate propulsion stage 44,
and a lower propulsion stage 46 adjacent the nosecone 36, stacked
longitudinally in that order for being ignited in the opposite
order. It will be appreciated that any suitable number of
propulsion stages may be utilized.
[0036] The propulsion stages 42, 44, and 46 contain propellant
enclosed therein, such as solid fuel or fluid fuel, including
liquid or gaseous fuel, or any combination thereof. Each of the
propulsion stages 42, 44, and 46 may include the same propellant
as, or a propellant different from, any other of the propulsion
stages 42, 44, and 46. Each stage 42, 44, and 46 also includes a
booster for storing the propellant and a nozzle operatively coupled
to the booster for expelling pressurized gases produced by burning
the propellant. For example, a lower nozzle 48 is operatively
coupled to a lower booster 50 of the lower propulsion stage 46.
[0037] The propulsion stages 42, 44, and 46 may also include
fuselage flanges, such as flanges 62, 63, and 64, for coupling
propulsion stages to one another or for protecting projectile
systems. The flanges may also make the projectile 34 more
aerodynamic by providing a substantially uniform outer profile.
[0038] The flange 62 is integral with, such as attached to, the
propulsion stages 44 and 46. As shown, the flange 62 surrounds the
intermediary propulsion stage 44, and extends between a rear end 65
of the intermediary propulsion stage 44 and a forward end 66 of the
lower propulsion stage 46. Thus, the flange 62 provides an
extension of the propulsion stage 44, thereby providing structure
to enable coupling, such as by a ring and groove joint, of the
intermediary propulsion stage 44 to the lower propulsion stage
46.
[0039] Likewise, the flange 63 is integral with the propulsion
stages 42 and 44. The flange 63 surrounds the upper propulsion
stage 42 and extends toward the intermediary propulsion stage 44.
The flange 64 is integral with the lower propulsion stage 46 and
protects projectile systems, such as the lower integrated actuation
system 68, to be further discussed later.
[0040] The projectile further includes an integrated actuation
system operatively coupled to each of the propulsion stages 42, 44,
and 46 for storing and releasing propellant or pressurant, herein
referred to jointly as propellant, such as methane, or any other
suitable propellant. Through release of the propellant from the
integrated actuation system, thrust vector may be controlled via
manipulation of the direction of thrust from the propulsion stage.
Attitude may also be controlled via the release of the propellant,
thus altering orientation of the projectile with respect to an
inertial frame of reference. For example, a lower integrated
actuation system 68 for controlling thrust vector and attitude is
operatively coupled to the lower propulsion stage 46, and will be
discussed in greater detail with reference to FIGS. 3-7. Any number
of integrated actuation systems may be utilized in conjunction with
any number of propulsion stages, and the one or more integrated
actuation systems may be located in any suitable location of the
projectile. The propellant stored in the integrated actuation
systems may be the same propellant stored in any of the propulsion
stages 42, 44, and 46, or it may be a different propellant.
[0041] The projectile 34 may also include a guidance and control
system, such as a controller 70. The controller 70 may be mounted
in the nosecone 36, included in the flight vehicle 40, or otherwise
located in another suitable location of the projectile 34. The
controller 70 is communicatively coupled to the propulsion stages
42, 44, and 46 for controlling timing of ignition of the propellant
within the stages and for directing the projectile 34 towards a
desired destination. The controller 70 is also communicatively
coupled to the integrated actuation systems, such as the integrated
actuation system 68, for controlling the integrated actuation
system 68, and thereby controlling thrust vector and attitude of
the projectile 34. The controller 70 may utilize a variety of
different data in order to direct the projectile 34. As an example,
the desired destination of the projectile 34 may be a location of a
target, and more specifically, the desired destination may be a
continually changing location of a moving target, such as a
ballistic missile.
[0042] A communications connection 72, such as a wire or fiber
optic cable, extends longitudinally along the projectile 34 between
the controller 70 and the propulsion stages and integrated
actuation systems, thereby allowing communication therebetween.
Alternatively, the projectile 34 may also include additional
communications connections, or the communications connection 72 may
be omitted and communication may instead be wireless or of any
other suitable type.
[0043] Turning now to FIGS. 3-7, the integrated actuation system 68
is shown in detail. The integrated actuation system 68 includes a
storage tank, such as a storage reservoir 80, for storing the
propellant, which may be in solid form or fluid form, such as gas
or liquid form, or any combination thereof. The propellant may also
be in a pressurized state. The storage reservoir 80 has a toroidal
shape and extends circumferentially around the nozzle 48, such as
surrounding an upper portion of the nozzle 48. Alternatively, the
storage reservoir 80 may be of any suitable shape and located in
another suitable location of the projectile 34. Additional storage
reservoirs may also be included or the storage reservoir 80 may be
operatively connected to an adjacent propulsion stage for
selectively siphoning propellant from the propulsion stage into the
storage reservoir 80.
[0044] The projectile 34 may also include a gas generator (not
shown separately) integral with the storage reservoir 80 and
located at least partially internal to the storage reservoir 80.
The gas generator, such as a warm or cold gas generator, is
integral with the storage reservoir 80 for burning a liquid or
solid propellant to produce gases for release into the integrated
actuation system 68 and for subsequent delivery to portions of the
projectile 34 for providing thrust vector and attitude control.
[0045] Numerous supply channels, such as a first or initial set of
supply channels 81 and a second or auxiliary set of supply channels
82, are connected to the storage reservoir 80. The sets of supply
channels 81 and 82 provide flow or fluid communication, including
gaseous communication, liquid communication, or any combination of
the two, between the storage reservoir 80 and outlets of the sets
of supply channels 81 and 82. Each set of supply channels 81 and 82
may include any number of supply channels, and the sets of supply
channels 81 and 82 may be fluidly interconnected. The sets of
supply channels 81 and 82 include valves 84 for controlling the
fluid flow and for allowing the integrated actuation system 68 to
selectively direct propellant to the outlets. The valves 84 may be
controlled by the control system 70 or any other suitable control
system. The outlets of the integrated actuation system 68 allow for
delivery of propellant into the nozzle 48 and to an external
periphery 92 of the projectile 34.
[0046] Interiorly-located outlets 94 of the first set of supply
channels 81 open to an internal periphery 96 of the nozzle 48 for
changing a direction of the thrust plume 100, thereby maneuvering
or diverting the projectile 34. In this way, the integrated
actuation system 68 serves as a thrust vector control subsystem.
Accordingly, burning of the propellant in the booster 50 of the
lower propulsion stage 46 causes the thrust plume 100 to be
outwardly directed from the nozzle 48. Upon release of propellant
from the storage reservoir 80, or burning of liquid or solid
propellant in the storage reservoir 80 via the gas generator to
produce propellant gas, the resulting propellant is delivered
through one or more channels of the first set of supply channels 81
to the interiorly-located outlets 94 via opening of associated
valves 84 in the first set of supply channels 81. Injection or
release of an auxiliary plume 102 of the resulting propellant from
one or more of the interiorly-located outlets 94 and flow into the
nozzle 48 causes the direction or angle of the thrust plume 100 to
be altered. The direction or angle of the thrust plume 100 is
altered via interaction, such as kinetic, chemical, or thermal
interaction, or any combination of any of the three, of the
auxiliary plume 102 with the thrust plume 100.
[0047] Use of propellant from the storage reservoir 80 to direct
the thrust plume 100 provides advantages over other thrust
vectoring methods, such as the use of gimbaled nozzles. Typical
gimbaled nozzles involve flex seals or ball and socket joints so
the nozzle may be gimbaled upon thrust vector control actuation.
Both flex seals and ball and socket joints are temperature
sensitive, limiting thrust vector control performance and leading
in many cases to nozzle failures. Both types of gimbaled systems
require a series of material layers that thermally expand at
different rates during the inter-pulse delay, when the heat from
the first pulse burn soaks though the nozzle material layers.
Additionally, debonding, cracking, and delamination may ensue
resulting in nozzle failure when the second pulse is ignited. As
such, the thrust vector control subsystem of the integrated
actuation system 68 mitigates these issues by integrating the
thrust vector controls into the system 68, enabling greater
survivability and better performance of the thrust vector
controls.
[0048] Peripherally-located outlets 110 of the second set of supply
channels 82 open to the external periphery 92 of the projectile 34
at external openings 102 defined by the flange 64. As shown, the
peripherally-located outlets 110 open in a direction substantially
orthogonal to a direction of the thrust from the nozzle 48,
although they may open in any other suitable direction. Release of
propellant through the outlets 110 produces additional thrust,
thereby maneuvering or diverting the projectile 34, such as by
altering attitude, flight angle, or roll of the projectile 34. In
this way, the integrated actuation system 68 serves as an attitude
control subsystem. Accordingly, upon release of resulting
propellant gas from the storage reservoir 80 of the integrated
actuation system 68, the propellant gas flows into the second set
of supply channels 82. Upon opening of associated valves 84 in the
second set of supply channels 82, an auxiliary plume 102 of the
resulting propellant is released from one or more
peripherally-located outlets 110, enabling attitude and/or roll
control of the projectile 34.
[0049] The projectile 34 has numerous advantages over projectiles
having non-integrated or uncombined systems, such as uncombined
thrust vector control and attitude control subsystems. The
integration of control subsystems to a single actuation source,
such as the propellant of the integrated actuation system 68,
results in a significant deletion of redundant hardware, such as
passages, actuators, and batteries. The integrated actuation system
68 also enables efficient manufacture and reliability at a lower
cost. For instance the system 68 reduces part count and simplifies
assembly integration with a projectile thereby increasing
reliability. Combining these critical control subsystems may also
reduce weight and eliminate many single point failure sources,
which are desired traits for deployment and performance of
projectiles, such as missiles.
[0050] Projectiles using the integrated actuation system 68 also
have greater mission flexibility. For example, the lower propulsion
stage 46 may have more compact hardware due to integration of
systems, and thus may provide more longitudinal volume for more
booster propellant. This may be particularly important for length
constrained, encanistered missiles, such as ballistic missile
defense interceptors.
[0051] Integration of the power actuation sources for the entire
system--using the propellant in the storage reservoir 80--also
achieves efficient power source utilization. As compared with
projectiles having separate control subsystems, and therefore
increased wasted or unused power source, the integrated actuation
system 68 wastes minimal power source. For instance, excess
propellant not used by the initial thrust vector control operation
is available for other control subsystem operations, such as
attitude control operation, providing more flexibility for longer
interceptor coast or aerodynamic maneuvering after lower propulsion
stage booster burn out.
[0052] Turning now to FIGS. 8-11, another exemplary projectile 120
having an integrated actuation system 124 is shown. The integrated
actuation system 124 may be used in place of the integrated
actuation system 68 (FIGS. 1-7), and the discussion below omits
many features of the projectile 120 and integrated actuation system
124 that are similar to those of the projectile 34 (FIGS. 1-7) and
associated integrated actuation system 68. In addition, features of
the integrated actuation system 124 may be combined with those of
the integrated actuation system 68.
[0053] As shown, the integrated actuation system 124 is in fluid
communication with a nozzle actuation system 130 for positioning or
moving, such as rotating or extending, a nozzle 132 of the
projectile 120. Thus in addition to supply channels for selectively
directing propellant to the nozzle 132 and to the external
periphery 128 of the projectile 120, the integrated actuation
system 124 may have a set of supply channels 136, in turn having
valves 140, for selectively directing propellant from the storage
reservoir 134 to the nozzle actuation system 130. The nozzle
actuation system 130 may include actuators 142, such as
piston-cylinder assemblies, for extending the nozzle 132 from a
retracted position (FIGS. 8 and 9) to an extended position (FIGS.
10 and 11). The actuators 142 may also include a locking mechanism,
such as a lock 143, for locking the actuator 142 in the extended
position after initial propellant flow from the storage reservoir
134.
[0054] Accordingly, delivery of propellant from the storage
reservoir 134 to one or more actuators 142 may cause the one or
more actuators 142 to extend. Extension of the actuators 142
thereby causes an outer cuff 144 of the nozzle 132 to extend
axially away from an inner cuff 146. In this way, the outer cuff
144 extends axially away from the inner cuff 146 between the
retracted position, where the outer cuff 144 is located around the
inner cuff 146, and the extended position. At the extended
position, a rear end 150 of the outer cuff 144 extends from the
rear end 152 of the projectile 120. Also in the extended position,
a forward end 154 of the outer cuff 144 mates with a rear end 156
of the inner cuff 146, providing a seal between the inner and outer
cuffs 146 and 144. Alternatively, the inner and outer cuffs 146 and
144 may be separated from one another with the forward end 154
located adjacent the rear end 156.
[0055] As compared with typical nozzle extension systems, the
nozzle actuation system 130 is not actuated by electro-mechanical
actuators with separate batteries. Instead, the nozzle actuation
system 130 of the integrated actuation system 124 uses high
pressure propellant from the same storage reservoir as the thrust
vector control and attitude control subsystems of the integrated
actuation system 124.
[0056] FIGS. 12-14 show another exemplary projectile 220 having an
integrated actuation system 224. The integrated actuation system
224 may be used in place of any other integrated actuation system
described herein and/or features of the integrated actuation
systems may be combined.
[0057] As shown, the integrated actuation system 224 is in fluid
communication with a stage separation system 230 for separating
portions of the projectile 220 from one another. For example, the
stage separation system 230 may enable a lower propulsion stage 232
to separate from a remainder of the projectile 224 upon exhaustion
of propellant contained in the propulsion stage 232. It will be
appreciated that the stage separation system 230 may be included to
separate any portion of the projectile 220 from the remainder of
the projectile 220.
[0058] In addition to sets of supply channels for selectively
directing propellant to the nozzle 226 and to the external
periphery 228 of the projectile 220, the integrated actuation
system 224 may have a set of supply channels 236, in turn having
valves 240, for selectively directing propellant from the storage
reservoir 234 to the stage separation system 230. The stage
separation system 230 may include a passage 242 providing fluid
communication between the channels 236 and a separation cavity 244
of the stage separation system 230. The separation cavity 244 may
be defined by a wall 250 of the fuselage flange 252, and the wall
250 may have a frangible portion 254. Alternatively, the passage
242 may be operatively coupled to the frangible portion 254 and the
cavity 244 may be omitted.
[0059] Upon actuation of the stage separation system 230, including
delivery of propellant from the storage reservoir 234 to the cavity
244 and frangible portion 254, the frangible portion 254 is caused
to break via kinetic, chemical, or thermal interaction, or any
combination of the three. In this way, the fuselage flange 252 may
be fractured such that the lower propulsion stage 232 is allowed to
separate from the remainder of the projectile 220. One or more
stage separation systems 230 may be operatively coupled to the
integrated actuation system 224 to provide for breaking of numerous
frangible portions 254, thus enabling separation of the lower
propulsion stage 232.
[0060] The stage separation system 230 of the integrated actuation
system 224 provides for less variable separation characteristics
than a typical pyrotechnic device, particularly during a stage in a
projectile's flight when the projectile is prone to aerodynamic
instability. Such typical pyro-initiated devices require internal
fail-safe electronics and multiple batteries, increasing design
complexity, assembly complications, cost, weight, and failure
points of the projectile. The high number of pyro-initiated devices
and power supplies necessary to separate a propulsion stage from a
remainder of the projectile will also require more communication
cabling and routing challenges, increasing further the projectile
weight and cost. As such, the present invention provides an
alternative system incorporating more efficient manufacture and
reliability, and providing for reduced risk.
[0061] Turning now to FIGS. 15 and 16, another exemplary projectile
320 having an integrated actuation system 324 is shown. The
integrated actuation system 320 may be used in place of any other
integrated actuation system described herein and/or features of the
integrated actuation systems may be combined.
[0062] As shown, the integrated actuation system 324 includes a
power generator, such as an electrical generator 326, coupled
between a storage reservoir 330 and a manifold 340, providing fluid
communication between the two. The electric generator 326, such as
a turbine generator, may be used to generate power for the
projectile 320. Accordingly, high pressure propellant gases in the
storage reservoir 330 may be flashed down to a lower pressure upon
entering the manifold 340, thereby transferring kinetic energy to
the generator 326 and generating power for other systems of the
projectile 320, such as a guidance system controller (not shown).
In this way, the need for batteries or other power sources in the
projectile is reduced or possibly eliminated.
[0063] It will be appreciated that any of the above-mentioned
integrated actuation systems may provide for propellant flow
between the associated storage reservoirs and any combination of
the nozzle actuation system 130 (FIG. 8), stage separation system
230 (FIG. 12), interiorly-located outlets 94 (FIG. 7),
peripherally-located outlets 110 (FIG. 7), and manifold 340 and
generator 326 (FIG. 15), while omitting propellant flow between any
of the listed elements not included in the combination.
[0064] Although the invention has been shown and described with
respect to a certain embodiment or embodiments, it is obvious that
equivalent alterations and modifications will occur to others
skilled in the art upon the reading and understanding of this
specification and the annexed drawings. In particular regard to the
various functions performed by the above described elements
(components, assemblies, devices, compositions, etc.), the terms
(including a reference to a "means") used to describe such elements
are intended to correspond, unless otherwise indicated, to any
element which performs the specified function of the described
element (i.e., that is functionally equivalent), even though not
structurally equivalent to the disclosed structure which performs
the function in the herein illustrated exemplary embodiment or
embodiments of the invention. In addition, while a particular
feature of the invention may have been described above with respect
to only one or more of several illustrated embodiments, such
feature may be combined with one or more other features of the
other embodiments, as may be desired and advantageous for any given
or particular application.
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